Airworthiness Directives; The Boeing Company Airplanes, 40508-40511 [2017-17538]

Download as PDF 40508 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k)(1) of this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. pmangrum on DSK3GDR082PROD with PROPOSALS (k) Related Information (1) For more information about this AD, contact Eric Igama, Aerospace Engineer, Systems and Equipment Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5388; fax: 562–627–5210; email: roderick.igama@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 Issued in Renton, Washington, on August 16, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–17839 Filed 8–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0778; Product Identifier 2017–NM–038–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 757–200 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the side panel-to-frame attachments and frames of the aft cargo compartment are subject to widespread fatigue damage (WFD). This proposed AD would require an inspection of the side panel-to-frame attachments and frames to verify that certain modifications have been done, and applicable on-condition actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by October 10, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; SUMMARY: PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017–0778. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0778; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Muoi Vuong, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5205; fax: 562–627– 5210; email: Muoi.Vuong@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0778; Product Identifier 2017– NM–038–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a E:\FR\FM\25AUP1.SGM 25AUP1 40509 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. Any frame crack at the attachment points of the side panel-to-frame attachments of the aft cargo compartment could go undetected and grow in length. This condition could result in reduced structural integrity of the body frames, and consequent rapid decompression of the airplane. and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017. The service information describes procedures for a general visual inspection of the side panel-to-frame attachments and frames to verify that certain modifications have been done. The service information also describes procedures for on-condition actions, which include repetitive inspections for cracking, repairs, and modifications. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Explanation of Compliance Time FAA’s Determination We are proposing this AD because we evaluated all the relevant information Proposed AD Requirements This proposed AD would require accomplishment of the actions identified as ‘‘RC’’ (required for compliance) in the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017, described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0778. The compliance time for the replacement specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is replaced before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 13 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost General visual inspection ................................ 1 work-hour × $85 per hour = $85 ................. pmangrum on DSK3GDR082PROD with PROPOSALS We estimate the following costs to do any necessary on-condition actions that would be required. We have no way of Cost per product Parts cost $0 Cost on U.S. operators $85 $1,105 determining the number of aircraft that might need these on-condition actions. ESTIMATED COSTS OF ON-CONDITION ACTIONS * Labor cost Parts cost Up to 45 work-hours × $85 per hour = Up to $3,825 ..................................................................... Unavailable ................ Cost per product Up to $3,825. * The costs in the table do not include the cost estimate for on-condition repairs. We have received no definitive data that would enable us to provide cost estimates for the on-condition repairs specified in this proposed AD. VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\25AUP1.SGM 25AUP1 40510 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules pmangrum on DSK3GDR082PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2017–0778; Product Identifier 2017– NM–038–AD. (a) Comments Due Date We must receive comments by October 10, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 757–200 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating that the side panel-to-frame attachments and frames of the aft cargo compartment are subject to widespread fatigue damage. We are issuing this AD to prevent fatigue cracking at the attachment points of the side panel-toframe attachments of the aft cargo compartment, which could result in reduced structural integrity of the body frames, and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) One-Time General Visual Inspection and Corrective Actions Except as required by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017, do all applicable actions identified as ‘‘RC’’ (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 (h) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD, the phrase ‘‘the effective date of this AD’’ may be substituted for ‘‘the Revision 1 date of this service bulletin,’’ as specified in Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017. (2) Where Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017, specifies contacting Boeing, and specifies that action as RC: This AD requires using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) Terminating Action for Inspections Accomplishment of a modification in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757–53A0012, Revision 1, dated January 25, 2017, terminates the inspections required by paragraph (g) of this AD at the modified location only. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (k)(1) of this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h)(2) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, E:\FR\FM\25AUP1.SGM 25AUP1 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: (k) Related Information • Federal eRulemaking Portal: Go to (1) For more information about this AD, http://www.regulations.gov. Follow the contact Muoi Vuong, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO instructions for submitting comments. Branch, 3960 Paramount Boulevard, • Fax: 202–493–2251. Lakewood, CA 90712–4137; phone: 562–627– • Mail: U.S. Department of 5205; fax: 562–627–5210; email: Transportation, Docket Operations, M– Muoi.Vuong@faa.gov. 30, West Building Ground Floor, Room (2) For service information identified in W12–140, 1200 New Jersey Avenue SE., this AD, contact Boeing Commercial Washington, DC 20590. Airplanes, Attention: Contractual & Data • Hand Delivery: Deliver to Mail Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; address above between 9 a.m. and 5 telephone 562–797–1717; Internet https:// p.m., Monday through Friday, except www.myboeingfleet.com. You may view this Federal holidays. referenced service information at the FAA, For service information identified in Transport Standards Branch, 1601 Lind this NPRM, contact Boeing Commercial Avenue SW., Renton, WA. For information Airplanes, Attention: Contractual & Data on the availability of this material at the Services (C&DS), 2600 Westminster FAA, call 425–227–1221. Blvd., MC 110–SK57, Seal Beach, CA Issued in Renton, Washington, on August 90740–5600; telephone 562–797–1717; 10, 2017. Internet https:// Dionne Palermo, www.myboeingfleet.com. You may view Acting Director, System Oversight Division, this referenced service information at Aircraft Certification Service. the FAA, Transport Standards Branch, [FR Doc. 2017–17538 Filed 8–24–17; 8:45 am] 1601 Lind Avenue SW., Renton, WA. BILLING CODE 4910–13–P For information on the availability of this material at the FAA, call 425–227– DEPARTMENT OF TRANSPORTATION 1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. Federal Aviation Administration FAA–2017–0779. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2017–0779; Product Identifier 2017–NM–040–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This proposed AD was prompted by reports of degraded bondline performance of co-bonded upper wing stringer-to-skin joints. This proposed AD would require repetitive inspections of certain upper wing stringers for any disbond and corrective actions, if necessary; and a terminating preventative modification of installing disbond arrestment (DBA) fasteners. This proposed AD would also require revising the inspection or maintenance program to incorporate an airworthiness limitation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by October 10, 2017. pmangrum on DSK3GDR082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0779; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6487; fax: 425–917–6590; email: allen.rauschendorfer@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0779; Product Identifier 2017– PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 40511 NM–040–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of degraded bond-line performance of co-bonded upper wing stringer-to-skin joints. The co-bonded upper wing stringer-to-skin joints were determined to have degraded bond-line performance due to the exposure of the bond surface with the use of BMS 8–308 peel ply to cure times that exceeded 4 hours at a temperature of 345 degrees Fahrenheit (F) plus or minus 10 F. The upper wing stringer-to-skin joint disbonding can reduce the structural capability to where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We have reviewed Boeing Alert Service Bulletin B787–81205– SB570030–00, Issue 001, dated March 17, 2017 (‘‘ASB B787–81205– SB570030–00, Issue 001’’). This service information describes procedures for inspection of certain upper wing stringers for any disbond and repairs; and for a preventative modification which consists of, depending on airplane configuration, applying copper foil to the upper wing at certain stringer and rib bay locations, installing DBA fasteners on the upper flanges of the upper wing stringers at the stringer and rib bay locations, applying cap seals to the DBA fasteners, and applying edge sealant to the stringers at the DBA fastener installation locations. We have also reviewed Airworthiness Limitation (AWL) 57–AWL–13, ‘‘Inspection Requirements for In-Tank Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener Installations of Lightning Zone 2,’’ of Boeing 787 Special Compliance Items/ Airworthiness Limitations, D011Z009– 03–04, dated February 2017. This service information describes tasks for inspecting in-tank fasteners and edge seals near DBA fastener installations of lightning zone 2. E:\FR\FM\25AUP1.SGM 25AUP1

Agencies

[Federal Register Volume 82, Number 164 (Friday, August 25, 2017)]
[Proposed Rules]
[Pages 40508-40511]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17538]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0778; Product Identifier 2017-NM-038-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 757-200 series airplanes. This 
proposed AD was prompted by an evaluation by the design approval holder 
(DAH) indicating that the side panel-to-frame attachments and frames of 
the aft cargo compartment are subject to widespread fatigue damage 
(WFD). This proposed AD would require an inspection of the side panel-
to-frame attachments and frames to verify that certain modifications 
have been done, and applicable on-condition actions. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by October 10, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may 
view this referenced service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221. It is 
also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-0778.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0778; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Muoi Vuong, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5205; fax: 562-627-
5210; email: Muoi.Vuong@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0778; 
Product Identifier 2017-NM-038-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a

[[Page 40509]]

lap splice joining two large skin panels. Widespread damage can also 
occur in multiple elements such as adjacent frames or stringers. 
Multiple-site damage and multiple-element damage cracks are typically 
too small initially to be reliably detected with normal inspection 
methods. Without intervention, these cracks will grow, and eventually 
compromise the structural integrity of the airplane. This condition is 
known as widespread fatigue damage. It is associated with general 
degradation of large areas of structure with similar structural details 
and stress levels. As an airplane ages, WFD will likely occur, and will 
certainly occur if the airplane is operated long enough without any 
intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    Any frame crack at the attachment points of the side panel-to-frame 
attachments of the aft cargo compartment could go undetected and grow 
in length. This condition could result in reduced structural integrity 
of the body frames, and consequent rapid decompression of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 757-53A0012, Revision 1, 
dated January 25, 2017. The service information describes procedures 
for a general visual inspection of the side panel-to-frame attachments 
and frames to verify that certain modifications have been done. The 
service information also describes procedures for on-condition actions, 
which include repetitive inspections for cracking, repairs, and 
modifications.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishment of the actions 
identified as ``RC'' (required for compliance) in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0012, Revision 1, 
dated January 25, 2017, described previously, except for any 
differences identified as exceptions in the regulatory text of this 
proposed AD.
    For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2017-0778.

Explanation of Compliance Time

    The compliance time for the replacement specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is replaced before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Costs of Compliance

    We estimate that this proposed AD affects 13 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
General visual inspection..........  1 work-hour x $85 per hour               $0             $85          $1,105
                                      = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required. We have no way of determining the 
number of aircraft that might need these on-condition actions.

                                    Estimated Costs of On-Condition Actions *
----------------------------------------------------------------------------------------------------------------
              Labor cost                             Parts cost                        Cost per product
----------------------------------------------------------------------------------------------------------------
Up to 45 work-hours x $85 per hour =    Unavailable........................  Up to $3,825.
 Up to $3,825.
----------------------------------------------------------------------------------------------------------------
* The costs in the table do not include the cost estimate for on-condition repairs. We have received no
  definitive data that would enable us to provide cost estimates for the on-condition repairs specified in this
  proposed AD.


[[Page 40510]]

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2017-0778; Product Identifier 
2017-NM-038-AD.

(a) Comments Due Date

    We must receive comments by October 10, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 757-200 series 
airplanes, certificated in any category, as identified in Boeing 
Alert Service Bulletin 757-53A0012, Revision 1, dated January 25, 
2017.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder indicating that the side panel-to-frame attachments and 
frames of the aft cargo compartment are subject to widespread 
fatigue damage. We are issuing this AD to prevent fatigue cracking 
at the attachment points of the side panel-to-frame attachments of 
the aft cargo compartment, which could result in reduced structural 
integrity of the body frames, and consequent rapid decompression of 
the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) One-Time General Visual Inspection and Corrective Actions

    Except as required by paragraph (h) of this AD: At the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 757-53A0012, Revision 1, dated January 
25, 2017, do all applicable actions identified as ``RC'' (required 
for compliance) in, and in accordance with, the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0012, Revision 
1, dated January 25, 2017.

(h) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD, the phrase ``the effective date of this AD'' may be 
substituted for ``the Revision 1 date of this service bulletin,'' as 
specified in Boeing Alert Service Bulletin 757-53A0012, Revision 1, 
dated January 25, 2017.
    (2) Where Boeing Alert Service Bulletin 757-53A0012, Revision 1, 
dated January 25, 2017, specifies contacting Boeing, and specifies 
that action as RC: This AD requires using a method approved in 
accordance with the procedures specified in paragraph (j) of this 
AD.

(i) Terminating Action for Inspections

    Accomplishment of a modification in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A0012, Revision 1, dated January 25, 2017, terminates the 
inspections required by paragraph (g) of this AD at the modified 
location only.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your 
request to your principal inspector or local Flight Standards 
District Office, as appropriate. If sending information directly to 
the manager of the certification office, send it to the attention of 
the person identified in paragraph (k)(1) of this AD. Information 
may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Los Angeles ACO Branch, to make those findings. To be 
approved, the repair method, modification deviation, or alteration 
deviation must meet the certification basis of the airplane, and the 
approval must specifically refer to this AD.
    (4) Except as required by paragraph (h)(2) of this AD: For 
service information that contains steps that are labeled as RC, the 
provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps,

[[Page 40511]]

including substeps and identified figures, can still be done as 
specified, and the airplane can be put back in an airworthy 
condition.

(k) Related Information

    (1) For more information about this AD, contact Muoi Vuong, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5205; fax: 562-627-5210; email: Muoi.Vuong@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 1601 Lind Avenue 
SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on August 10, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-17538 Filed 8-24-17; 8:45 am]
 BILLING CODE 4910-13-P